Abstract
Aeroelastic properties of two-dimensional panels neglecting and considering the shear deformation in supersonic airflow are analytically investigated. The two types of panel are known as the Kirchhoff and Mindlin panels. A method for estimating the flutter bound of the aeroelastic structural system is proposed. The classical plate theory and the first-order shear deformation theory are used in the structural modeling. The unsteady aerodynamic pressure is evaluated by the supersonic piston theory. The governing equation of motion of the structural system is formulated applying Hamilton’s principle. The exact solution for the partial differential equation of motion of the aeroelastic structural system is calculated, and the aeroelastic modes (AEMs) of the panels are obtained and compared with the vacuo natural modes of the structures. The correctness of the present methodology used in the aeroelastic analysis is verified. Aeroelastic characteristics of panels with different boundary conditions are investigated, and the time response history of the panel is calculated using the AEMs obtained in this study. Moreover, the accuracy of the assumed mode method in the aeroelastic analysis is also researched. Some interesting and useful results are obtained and analyzed.
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